Thruster for micro-satellite and manufacturing method thereof

Patent metadata

Field	Value
Publication number	US-2025091733-A1
Application number	US-202418827975-A
Country	US
Kind code	A1
Filing date	Sep 9, 2024
Priority date	Sep 15, 2023
Publication date	Mar 20, 2025
Grant date	—

Abstract

A thruster for a micro-satellite according to an embodiment of the present disclosure includes a first thrust module configured to generate a first thrust in a first direction, a second thrust module configured to generate a second thrust in a second direction intersecting the first direction, and a control substrate on which the first thrust module and the second thrust module are mounted, the control substrate being configured to control the first thrust module and the second thrust module, in which the first thrust module and the second thrust module includes a plurality of printed circuit boards stacked.

First claim

What is claimed is:

1 . A thruster for a micro-satellite, the thruster comprising:
a first thrust module configured to generate a first thrust in a first direction; a second thrust module configured to generate a second thrust in a second direction intersecting the first direction; and a control substrate on which the first thrust module and the second thrust module are mounted, the control substrate being configured to control the first thrust module and the second thrust module, wherein the first thrust module and the second thrust module comprises a plurality of printed circuit boards stacked.

2 . The thruster of claim 1 , wherein:
the first thrust module comprises: a first substrate assembly comprising the plurality of printed circuit boards; a first injector installed in the first substrate assembly and configured to inject a propellant; a first catalyst chamber installed in the first substrate assembly and connected to the first injector, a catalyst being positioned in the first catalyst chamber; and a first nozzle installed in the first substrate assembly and configured to generate the first thrust by discharging a first thrust gas, which is generated from the first catalyst chamber, to the outside of the first substrate assembly.

3 . The thruster of claim 2 , wherein:
the second thrust module comprises: a second substrate assembly including the plurality of printed circuit boards; a second injector installed in the second substrate assembly and configured to inject a propellant; a second catalyst chamber installed in the second substrate assembly and connected to the second injector; and a second nozzle installed in the second substrate assembly and configured to generate the second thrust by discharging a thrust gas, which is generated from the second catalyst chamber, to the outside of the second substrate assembly.

4 . The thruster of claim 3 , wherein:
the first injector and the second injector are formed by stacking a plurality of injector holes formed in the plurality of printed circuit boards.

5 . The thruster of claim 4 , wherein:
the first catalyst chamber and the second catalyst chamber are formed by stacking a plurality of chamber holes formed in the plurality of printed circuit boards.

6 . The thruster of claim 5 , wherein:
the first nozzle or the second nozzle is connected to any one of the plurality of chamber holes.

7 . The thruster of claim 1 , further comprising:
the second thrust module and the first thrust module further comprise couplers coupled to the control substrate.

8 . A method of manufacturing a thruster for a micro-satellite, the method comprising:
manufacturing a first thrust module, which is configured to generate a first thrust in a first direction, by stacking a plurality of printed circuit boards; manufacturing a second thrust module, which is configured to generate a second thrust in a second direction intersecting the first direction, by stacking the plurality of printed circuit boards; and coupling the first thrust module and the second thrust module onto a control substrate.

9 . The method of claim 8 , wherein:
the manufacturing of the first thrust module comprises: forming a bonding agent pattern on a conductive layer of the plurality of printed circuit boards; aligning and stacking some of the plurality of printed circuit boards; inserting a catalyst into a first catalyst chamber formed by stacking a plurality of chamber holes formed in some of the printed circuit boards; and coupling an uppermost printed circuit board onto some of the printed circuit boards, wherein a first nozzle, which is connected to the chamber hole and parallel to a surface of the printed circuit board, is installed in some of the printed circuit boards.

10 . The method of claim 9 , wherein:
in the inserting of the catalyst into the first catalyst chamber, a first catalyst withdrawal prevention member is inserted between the first nozzle and the first catalyst chamber installed in the printed circuit board, and the first catalyst withdrawal prevention member is installed to intersect an extension direction of the first nozzle.

11 . The method of claim 9 , wherein:
the manufacturing of the second thrust module comprises: forming a bonding agent pattern on a conductive layer of the plurality of printed circuit boards; aligning and stacking some of the plurality of printed circuit boards; inserting a catalyst into a second catalyst chamber formed by stacking a plurality of chamber holes formed in some of the printed circuit boards; and coupling an uppermost printed circuit board onto some of the printed circuit boards, wherein a second nozzle, which is connected to the chamber hole and perpendicular to a surface of the printed circuit board, is installed in some of the uppermost printed circuit board.

12 . The method of claim 11 , wherein:
in the inserting of the catalyst into the second catalyst chamber, a second catalyst withdrawal prevention member is inserted between the second nozzle and the second catalyst chamber installed in the uppermost printed circuit board, and the second catalyst withdrawal prevention member is installed to intersect an extension direction of the second nozzle.

13 . The method of claim 9 , wherein:
the forming of the bonding agent pattern comprises: aligning a metal mask having a plurality of opening portions on a conductive layer of the printed circuit board; and forming a bonding agent pattern by applying bonding agent paste on the conductive layer through the plurality of opening portions.

Assignees

• Postech Res & Business Dev Found

Inventors

• Lee Jeongrak
• Kim Seonghyeon
• Lee Anna

Classifications

• B64G1/26 Primary

  using jets · CPC title

• B64G1/40

  Arrangements or adaptations of propulsion systems · CPC title

• F02K9/52

  Injectors · CPC title

• F02K9/97

  Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title

• F02K9/80 Primary

  characterised by thrust or thrust vector control (burning control of solid propellants F02K9/26; feeding control of liquid or gaseous propellants F02K9/56; re-ignitable, restartable or intermittently operated rocket-engine plants F02K9/94) · CPC title